Variable slat displacement using spanwise actuator
By employing a span-wise oriented linear hydraulic slat actuator with a bell crank mechanism, the issue of accommodating actuators in thin aircraft wings is addressed, achieving enhanced slat movement and reduced structural penetration.
Patent Information
- Application Number
- JP2024108034
- Authority / Receiving Office
- JP · JP
- Patent Type
- Applications
- Current Assignee / Owner
- Priority Date
- 2023-09-07
- Filing Date
- 2024-07-04
- Publication Date
- 2025-03-19
AI Technical Summary
The challenge in aircraft wing design is to accommodate linear hydraulic slat actuators while maintaining a thin wing shape, as thinner wings restrict the movement and packaging of these actuators.
A span-wise oriented linear hydraulic slat actuator utilizing a bell crank mechanism to achieve variable power movement, allowing the actuator output link to move in different directions and enabling slats to retract and extend without penetrating the wing's front girder.
This configuration allows for greater movement of the slats within the aircraft wing architecture while occupying less space, avoiding the need to penetrate the wing's structure and enabling adjustable slat movement via the bell crank's arm length.
Smart Images
Figure 2025038865000001_ABST
Abstract
Description
[Technical field]
[0001]
[0001] This disclosure relates generally to aircraft wings, and more particularly to actuators that move slats on aircraft wings. [Background technology]
[0002]
[0002] This background discussion is provided for the purpose of broadly presenting the context of the present disclosure. Unless otherwise stated herein, no admission is made, expressly or impliedly, that the material described in this section is prior art to the present disclosure or the appended claims.
[0003]
[0003] To reduce the amount of drag associated with aircraft flight, aircraft wings are manufactured to be relatively thin. However, as aircraft wings become thinner, it becomes increasingly difficult to package various components within the aircraft wing. As a non-limiting example, as aircraft wing airfoils become smaller, it becomes more difficult to mount linear hydraulic slat actuators within the leading edge of an aircraft wing. Small aircraft wing airfoils typically require penetrations in the leading spar web to accommodate the length of the linear hydraulic slat actuator. However, in these scenarios, the actuator travel is severely limited. Summary of the Invention
[0004]
[0005] The present application is directed to a spanwise oriented linear hydraulic slat actuator that utilizes a bell crank to achieve variable output movement. For example, the linear hydraulic slat actuator may be coupled to a fixed structure of an aircraft wing. The linear hydraulic slat actuator is oriented spanwise along the aircraft wing. The bell crank is coupled to the linear hydraulic slat actuator and to an actuator output link. For example, a first arm of the bell crank is coupled to the linear hydraulic slat actuator and a second arm of the bell crank is coupled to the actuator output link. The linear hydraulic slat actuator uses spanwise movement to drive the first arm of the bell crank, which in turn moves the actuator output link in a different direction. This allows the aircraft wing slat to move between a retracted position and an extended position. For example, the aircraft wing slat is attached to the actuator output link. By driving a first arm of a bellcrank with a linear hydraulic slat actuator, the second arm of the bellcrank can move an actuator output link in a manner that retracts or extends the attached slat.
[0005]
[0006] Thus, by using a bell crank to move the actuator output link in a direction (e.g., chordwise) different from the spanwise movement of the linear hydraulic slat actuator, the linear hydraulic slat actuator may be oriented spanwise along the aircraft wing. As a result of the spanwise orientation, the linear hydraulic slat actuator may achieve greater movement within the aircraft wing architecture while occupying less space in the direction of slat movement (e.g., chordwise). As a result, penetration of the leading spar web within the aircraft wing may be avoided. Furthermore, for a linear hydraulic slat actuator with fixed travel, the output movement of the actuator output link, and therefore the movement of the attached slat, may be adjusted via the arm length of the bell crank.
[0006]
[0007] In one aspect, the present application discloses an aircraft wing. The aircraft wing includes a fixed structure and a linear hydraulic slat actuator attached to the fixed structure. The linear hydraulic slat actuator is oriented spanwise along the aircraft wing. The aircraft wing also includes an actuator output link and a slat attached to the actuator output link. The aircraft wing also includes a bell crank coupled to the linear hydraulic slat actuator and the actuator output link. In response to spanwise movement of the linear hydraulic slat actuator, the bell crank is configured to move the actuator output link in different directions, thereby enabling the slat to move between a retracted position and an extended position.
[0007]
[0008] In another aspect, the present application discloses a method of manufacturing an aircraft wing. The method includes mounting a linear hydraulic slat actuator to a fixed structure. The linear hydraulic slat actuator is oriented spanwise along the aircraft wing. The method also includes coupling a bell crank to the linear hydraulic slat actuator and coupling an actuator output link to the bell crank. The method also includes mounting a slat to the actuator output link. In response to spanwise movement of the linear hydraulic slat actuator, the bell crank moves the actuator output link in a different direction, which allows the slat to move between a retracted position and an extended position.
[0008]
[0009] In one aspect, the present application discloses an aircraft. The aircraft includes a fuselage and an aircraft wing attached to the fuselage. The aircraft wing includes a fixed structure and a linear hydraulic slat actuator attached to the fixed structure. The linear hydraulic slat actuator is oriented spanwise along the aircraft wing. The aircraft wing also includes an actuator output link and a slat attached to the actuator output link. The aircraft wing also includes a bell crank coupled to the linear hydraulic slat actuator and the actuator output link. In response to spanwise movement of the linear hydraulic slat actuator, the bell crank is configured to move the actuator output link in different directions, thereby enabling the slat to move between a retracted position and an extended position.
[0009]
[0010] The foregoing summary is for illustrative purposes only and is not intended to be in any way limiting. In addition to the exemplary aspects, embodiments, and features described above, further aspects, embodiments, and features will become apparent by reference to the drawings and the following detailed description.
[0010]
[0011] A more complete understanding of the embodiments of the present disclosure may be obtained by reference to the detailed description and claims in conjunction with the following drawings, in which like reference numbers indicate similar elements throughout. The numbers are provided to aid in understanding the disclosure and are not intended to limit the breadth, scope, scale, or applicability of the disclosure. The drawings are not necessarily drawn to scale. [Brief description of the drawings]
[0011] [Figure 1]
[0012] FIG. 1 illustrates a first view of a portion of an aircraft wing having spanwise oriented linear hydraulic slat actuators according to an illustrative embodiment. [Diagram 2]
[0013] FIG. 1 illustrates a second view of a portion of an aircraft wing having spanwise oriented linear hydraulic slat actuators according to an illustrative embodiment. [Diagram 3]
[0014] FIG. 1 illustrates a third view of a portion of an aircraft wing having spanwise oriented linear hydraulic slat actuators according to an illustrative embodiment. [Figure 4]
[0015] 1 illustrates a first view of a portion of a second aircraft wing having spanwise oriented linear hydraulic slat actuators according to an illustrative embodiment; [Diagram 5]
[0016] 1 illustrates a second view of a portion of a second aircraft wing having spanwise oriented linear hydraulic slat actuators in accordance with an illustrative embodiment; [Figure 6]
[0017] 1 illustrates an actuator output link operable to extend a slat between a retracted position and an extended position based on spanwise movement from a linear hydraulic slat actuator according to an exemplary embodiment. [Figure 7]
[0018] 1 illustrates a bell crank operable to move an actuator output link and a slat chordwise in response to spanwise movement from a linear hydraulic slat actuator according to an exemplary embodiment; [Figure 8]
[0019] 1 illustrates a bell crank in accordance with an illustrative embodiment. [Figure 9]
[0020] 1 is a flowchart of an example of an implementation of a method, according to an exemplary embodiment. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
[0012]
[0021] The drawings and the following description show several specific exemplary embodiments. Those skilled in the art will recognize that, even if not explicitly described or shown in the present specification, they may devise various configurations that embody the principles described herein and are included in the scope of the claims that follow this specification. Furthermore, any examples described herein are intended to aid in the understanding of the principles of the present disclosure and are not intended to be limiting. As a result, the present disclosure is not limited to the specific embodiments or examples described below, but is limited by the claims and their equivalents.
[0013]
[0022] Certain embodiments are described herein with reference to the drawings. In the description, common features may be designated by a common reference number throughout the drawings. In some drawings, multiple instances of a particular type of feature are used. Although these features are physically and / or logically different, the same reference number is used for each, and the different instances are distinguished by adding a letter to the reference number. When features as a group or type are referred to herein (e.g., when no particular one of the features is referred to), the reference number is used without the distinguishing letter. However, when one particular feature of a plurality of features of the same type is referred to herein, the reference number is used with the distinguishing letter. For example, a linear hydraulic slat actuator is indicated and associated with reference number 104. When referring to a particular one of the linear hydraulic slat actuators, such as linear hydraulic slat actuator 104A, the distinguishing letter "A" is used. However, when referring to any one of the linear hydraulic slat actuators or the linear hydraulic slat actuators as a group, the reference number 104 may be used without the distinguishing letter.
[0014]
[0023] As used herein, various terms are used for the purpose of describing particular embodiments only and are not intended to be limiting. For example, the singular forms "a / an" and "the" are intended to include the plural (unless the context clearly indicates otherwise). Furthermore, the terms "comprise", "comprises", and "comprising" may be used interchangeably with "include", "includes", or "including". Furthermore, the term "wherein" is used interchangeably with the term "where". As used herein, "exemplary" refers to an example, an implementation, and / or an aspect and should not be construed as limiting or as indicating a preferred or preferred embodiment. As used herein, ordinal terms (e.g., "first," "second," "third," etc.) modifying elements such as structures, components, operations, etc. do not in themselves indicate a priority or order of one element over another, but merely distinguish one element from other elements having the same name (apart from its use as an ordinal term). As used herein, the term "set" refers to a grouping of one or more elements, and the term "plurality" refers to a plurality of elements.
[0015]
[0024] Referring to FIG. 1, a first view of a portion of an aircraft wing 100 having spanwise oriented linear hydraulic slat actuators is shown in accordance with an exemplary embodiment.
[0016]
[0025] The aircraft wing 100 includes a fixed structure 102A. In FIG. 1, the fixed structure 102A corresponds to a support rib. However, in other embodiments, the fixed structure 102A may correspond to a leading spar or beam. A linear hydraulic slat actuator 104A is attached to the fixed structure 102A. The linear hydraulic slat actuator 104A is oriented spanwise 150 along the aircraft wing 100. For example, the linear hydraulic slat actuator 104A is oriented in such a way that a first end of the linear hydraulic slat actuator 104A faces the fuselage and a second end of the linear hydraulic slat actuator 104A faces the tip of the aircraft wing 100.
[0017]
[0026] The bellcrank 106A is coupled to the linear hydraulic slat actuator 104A and to the actuator output link 108A. In one embodiment shown in Figure 1, the fixed structure 102A is also coupled to the bellcrank 106A. In one embodiment shown in Figure 1, the fixed structure 102A is coupled to a pivot point 112 of the bellcrank 106A, which may correspond to a support rib coupled to the linear hydraulic slat actuator 104A.
[0018]
[0027] The bell crank 106A includes a first arm coupled to the linear hydraulic slat actuator 104A and a second arm coupled to the actuator output link 108A. A first length of the first arm defines a first bell crank radius (e.g., bell crank radius 120 in FIG. 1 ) and a second length of the second arm defines a second bell crank radius (e.g., bell crank radius 120). In one embodiment of FIG. 1 , the first length of the first arm is similar (e.g., equal) to the second length of the second arm, and thus the first bell crank radius is similar to the second bell crank radius. However, in other embodiments, the first bell crank radius may be different from the second bell crank radius, as described with respect to FIG. 8 .
[0019]
[0028] An input stroke length 130 associated with the linear hydraulic slat actuator 104A is based on a first bell crank radius (e.g., bell crank radius 120 in FIG. 1). The input stroke length 130 corresponds to the distance the linear hydraulic slat actuator 104A travels (e.g., extends or retracts). An output stroke length 140 associated with the actuator output link 108A is based on a second bell crank radius (e.g., bell crank radius 120 in FIG. 1). The output stroke length 140 corresponds to the distance the actuator output link 108A travels (e.g., moves). In some embodiments, as described in more detail with respect to FIG. 8, the second bell crank radius is greater than the first bell crank radius, such that the output stroke length 140 is greater than the input stroke length 130. In these embodiments, a smaller output stroke results in a larger movement of the linear hydraulic slat actuator, which in turn results in a smaller movement of the slat.
[0020]
[0029] In response to spanwise 150 movement of the linear hydraulic slat actuator 104A, the bell crank 106A can be configured to move the actuator output link 108A in a different direction (e.g., chordwise 152), thereby allowing a slat attached to the actuator output link 108A, such as slat 710 in FIG. 7, to move between a retracted position and an extended position.
[0021]
[0030] Thus, by using the bell crank 106A to move the actuator output link 108A in a direction (e.g., chordwise 152) different from the spanwise 150 movement of the linear hydraulic slat actuator 104A, the linear hydraulic slat actuator 104A can be oriented spanwise 150 along the aircraft wing 100. As a result of the spanwise 150 orientation, the linear hydraulic slat actuator 104A can achieve greater movement within the aircraft wing 100 while taking up less space in the direction of slat movement (e.g., chordwise 152). Furthermore, for a linear hydraulic slat actuator 104A with fixed movement, the output movement of the actuator output link 108A, and therefore the movement of the attached slat (e.g., slat 710 in FIG. 7), can be adjusted via the arm length of the bell crank 106A.
[0022]
[0031] Referring to Figure 2, a second view of a portion of an aircraft wing 100 having spanwise oriented linear hydraulic slat actuators is shown in accordance with an exemplary embodiment. In particular, Figure 2 shows a bottom view of linear hydraulic slat actuator 104A.
[0023]
[0032] The aircraft wing 100 includes a fixed structure 102A and a linear hydraulic slat actuator 104A mounted to the fixed structure 102A. The linear hydraulic slat actuator 104A is oriented spanwise 150 along the wing of the aircraft 100. The aircraft wing 100 also includes a bell crank 106A coupled to the linear hydraulic slat actuator 104A and to an actuator output link 108A.
[0024]
[0033] In response to spanwise 150 movement of the linear hydraulic slat actuator 104A, the bell crank 106A can be configured to move the actuator output link 108A in a different direction (e.g., chordwise 152), thereby allowing the slat 710 attached to the actuator output link 108A to move between a retracted position and an extended position.
[0025]
[0034] Thus, by using the bell crank 106A to move the actuator output link 108A in a direction (e.g., chordwise 152) different from the spanwise 150 movement of the linear hydraulic slat actuator 104A, the linear hydraulic slat actuator 104A can be oriented spanwise 150 along the aircraft wing 100. As a result of the spanwise 150 orientation, the linear hydraulic slat actuator 104A can achieve greater movement within the aircraft wing 100 while taking up less space in the direction of slat movement (e.g., chordwise 152). Furthermore, for a linear hydraulic slat actuator 104A with fixed movement, the output movement of the actuator output link 108A, and therefore the movement of the attached slat (e.g., slat 710 in FIG. 7), can be adjusted via the arm length of the bell crank 106A.
[0026]
[0035] 3, a third view of a portion of an aircraft wing 100 having spanwise oriented linear hydraulic slat actuators is shown in accordance with an exemplary embodiment. In particular, FIG. 3 shows a side view of actuator output link 108A.
[0027]
[0036] 1-2, in response to spanwise 150 movement of the linear hydraulic slat actuator 104A, the bell crank 106A may be configured to move the actuator output link 108A in a different direction (e.g., chordwise 152), thereby enabling a slat (not shown) attached to the actuator output link 108A to move between a retracted position and an extended position.
[0028]
[0037] Referring to FIG. 4, a first view of a portion of an aircraft wing 400 having spanwise oriented linear hydraulic slat actuators is shown in accordance with an exemplary embodiment.
[0029]
[0038] The aircraft wing 400 includes a fixed structure 102B. In Fig. 4, the fixed structure 102B corresponds to a support rib for the bell crank 106B. The linear hydraulic slat actuator 104B is oriented spanwise 450 along the aircraft wing 400. For example, the linear hydraulic slat actuator 104B is oriented in such a way that a first end of the linear hydraulic slat actuator 104B faces the fuselage and a second end of the linear hydraulic slat actuator 104B faces the tip of the aircraft wing 400.
[0030]
[0039] The bell crank 106B is coupled to the linear hydraulic slat actuator 104B and to the actuator output link 108B. In response to spanwise 450 movement of the linear hydraulic slat actuator 104B, the bell crank 106B may be configured to move the actuator output link 108B in a different direction (e.g., chordwise 452), thereby enabling a slat, such as slat 710 in FIG. 7, attached to the actuator output link 108B to move between a retracted position and an extended position.
[0031]
[0040] Thus, by using the bell crank 106B to move the actuator output link 108B in a direction (e.g., chordwise 452) different from the spanwise 450 movement of the linear hydraulic slat actuator 104B, the linear hydraulic slat actuator 104B may be oriented spanwise 450 along the aircraft wing 400. As a result of the spanwise 450 orientation, the linear hydraulic slat actuator 104B may achieve greater movement within the aircraft wing 400 while taking up less space in the direction of slat movement (e.g., chordwise 452).
[0032]
[0041] 5, a second view of a portion of an aircraft wing 400 having spanwise oriented linear hydraulic slat actuators is shown in accordance with an exemplary embodiment. In particular, FIG. 5 shows a side view of actuator output link 108B.
[0033]
[0042] 4, in response to spanwise 450 movement of the linear hydraulic slat actuator 104B, the bell crank 106B may be configured to move the actuator output link 108B in a different direction (e.g., chordwise 452), thereby allowing a slat (not shown) attached to the actuator output link 108B to move between a retracted position and an extended position.
[0034]
[0043] Referring to FIG. 6, an actuator output link 108C is shown operable to extend the slats between retracted and extended positions based on spanwise movement from a linear hydraulic slat actuator, according to an exemplary embodiment.
[0035]
[0044] In some embodiments, the actuator output link 108C may correspond to the actuator output link 108A. For example, in some embodiments, the actuator output link 108C may be coupled to a bell crank 106A, and in response to a spanwise 150 movement of the linear hydraulic slat actuator 104A, the bell crank 106A may be configured to move the actuator output link 108C in a different direction (e.g., chordwise 152). This allows a slat attached to the actuator output link 108C to move between a retracted position 610 and an extended position 620. In other embodiments, the actuator output link 108C may correspond to the actuator output link 108B. For example, in some embodiments, the actuator output link 108C may be coupled to a bell crank 106B, and in response to a spanwise 450 movement of the linear hydraulic slat actuator 104B, the bell crank 106B may be configured to move the actuator output link 108C in a different direction (e.g., chordwise 452). This allows the slat attached to the actuator output link 108C to move between a retracted position 610 and an extended position 620.
[0036]
[0045] Referring to FIG. 7, there is shown a bell crank operable to move the actuator output link and the slat chordwise in response to spanwise movement from a linear hydraulic slat actuator according to an example embodiment.
[0037]
[0046] 7, an aircraft wing 700 includes a fixed structure 102 (e.g., a support rib) and a linear hydraulic slat actuator 104. In some embodiments, the linear hydraulic slat actuator 104 may correspond to a linear hydraulic slat actuator 104A or a linear hydraulic slat actuator 104B. The linear hydraulic slat actuator 104 is oriented spanwise along the wing of the aircraft 700.
[0038]
[0047] The bell crank 106 is coupled to the linear hydraulic slat actuator 104 and to an actuator output link 108. In one embodiment shown in Figure 7, the fixed structure 102 is also coupled to the bell crank 106. In one embodiment shown in Figure 7, the fixed structure 102 may correspond to a support rib coupled to a pivot point of the bell crank 106.
[0039]
[0048] In response to spanwise movement of the linear hydraulic slat actuator 104, the bell crank 106 can be configured to move the actuator output link 108 in a different direction (e.g., chordwise), thereby allowing the slat 710 attached to the actuator output link 108C to move between a retracted position 610 and an extended position 620.
[0040]
[0049] Thus, by using the bell crank 106 to move the actuator output link 108C in a direction (e.g., chordwise) different from the spanwise movement of the linear hydraulic slat actuator 104, the linear hydraulic slat actuator 104 can be oriented spanwise along the aircraft wing 700. As a result of the spanwise orientation, the linear hydraulic slat actuator 104 can achieve greater movement within the aircraft wing 700 while taking up less space in the direction of slat movement (e.g., chordwise). Furthermore, for a linear hydraulic slat actuator 104 with fixed movement, the output movement of the actuator output link 108C, and therefore the movement of the attached slat 710, can be adjusted via the arm length of the bell crank 106.
[0041]
[0050] 8, a bell crank 800 is shown according to an example embodiment. Bell crank 800 may correspond to bell crank 106A, bell crank 106B, or bell crank 106.
[0042]
[0051] The bell crank 800 includes a first arm 810 and a second arm 820. The first arm 810 may be coupled to a linear hydraulic slat actuator, such as the linear hydraulic slat actuator 104A, the linear hydraulic slat actuator 104B, or the linear hydraulic slat actuator 104. The second arm 820 may be coupled to an actuator output link, such as the actuator output link 108A, the actuator output link 108B, or the actuator output link 108C. The first arm 810 may be configured to move from a first position 812 to a second position 814 in response to spanwise movement of the linear hydraulic slat actuator. The second arm 820 may be configured to move from a first position 822 to a second position 824 in response to movement from the first arm 810. For example, when the first arm 810 is in the first position 812, the second arm 820 is in the first position 822. However, when the first arm 810 is in the second position 814 , the second arm 820 is in the second position 824 .
[0043]
[0052] A first length of the first arm 810 defines a first bellcrank radius 816 and a second length of the second arm 820 defines a second bellcrank radius 826. An input stroke length 830 associated with the hydraulic slat actuator is based on the first bellcrank radius 816 and an output stroke length 840 associated with the actuator output link is based on the second bellcrank radius 826.
[0044]
[0053] The input stroke length 830 corresponds to the distance the linear hydraulic slat actuator 104 travels, and the output stroke length corresponds to the distance the actuator output link 108 travels. As shown in FIG. 8 , the second bell crank radius 826 is larger than the first bell crank radius 816, so that the output stroke length 840 is larger than the input stroke length 830. As a result, a small movement from the linear hydraulic slat actuator 104 can result in a larger movement from the actuator output link 108. Thus, in a linear hydraulic slat actuator 104 with constant travel, the output movement of the actuator output link 108, and therefore the movement of the attached slat 710, can be adjusted via the length of the arms 810, 820 of the bell crank 800.
[0045]
[0054] FIG. 9 illustrates a flow chart of a method 900 according to one embodiment of the present disclosure.
[0046]
[0055] The method 900 includes, at block 902, mounting a linear hydraulic slat actuator to a fixed structure. The linear hydraulic slat actuator is oriented spanwise along a wing of the aircraft. For example, referring to FIG. 1, a linear hydraulic slat actuator 104A is mounted to a fixed structure 102A. The linear hydraulic slat actuator 104A is oriented spanwise 150 along the wing of the aircraft 100.
[0047]
[0056] The method 900 also includes coupling the bellcrank to a linear hydraulic slat actuator at block 904. For example, with reference to Figure 1, the bellcrank 106A is coupled to the linear hydraulic slat actuator 104A.
[0048]
[0057] The method 900 also includes coupling the actuator output link to the bell crank at block 906. For example, with reference to Figure 1, actuator output link 108A is coupled to bell crank 106A.
[0049]
[0058] The method 900 also includes, at block 908, attaching the slat to an actuator output link. In response to spanwise movement of the linear hydraulic slat actuator, the bell cranks move the actuator output links in different directions. This allows the slat to move between a retracted position and an extended position. For example, referring to FIG. 7, a slat 710 is attached to the actuator output link 108C. In response to spanwise 150, 450 movement of the linear hydraulic slat actuators 104A, 104B, the bell cranks 106A, 106B may be configured to move the actuator output links 108A, 108B, 108C in different directions (e.g., chordwise 152). This allows the slat 710 attached to the actuator output links 108A, 108B, 108C to move between a retracted position 610 and an extended position 620. Thus, the linear hydraulic slat actuators 104A, 104B drive the bell cranks 106A, 106B.
[0050]
[0059] According to one embodiment of the method 900, the linear hydraulic slat actuators 104A, 104B are coupled to a first arm 810 of the bell crank 106A, 106B, 800 and the actuator output link 108A, 108B, 108C is coupled to a second arm 820 of the bell crank 106A, 106B, 800. A first length of the first arm 810 defines a first bell crank radius 816 and a second length of the second arm 820 defines a second bell crank radius 826.
[0051]
[0060] According to one embodiment of the method 900, the input stroke length 130, 830 associated with the linear hydraulic slat actuators 104A, 104B is based on a first bell crank radius 816, and the output stroke length 140, 840 associated with the actuator output links 108A, 108B, 108C is based on a second bell crank radius 826.
[0052]
[0061] According to one embodiment of method 900, the first bell crank radius is similar to the second bell crank radius. According to one embodiment of method 900, the first bell crank radius 816 is different from the second bell crank radius 826. As one non-limiting example, the second bell crank radius 826 is larger than the first bell crank radius 816. According to another embodiment, the second bell crank radius 826 can be smaller than the first bell crank radius 816.
[0053]
[0062] Thus, by using the bell cranks 106A, 106B, 800 to move the actuator output links 108A, 108B, 108C in a direction (e.g., chordwise 152, 452) different from the spanwise 150, 450 movement of the linear hydraulic slat actuators 104A, 104B, the linear hydraulic slat actuators 104A, 104B may be oriented in a spanwise 150, 450 direction along the aircraft wing 100, 400. As a result of the spanwise 150, 450 orientation, the linear hydraulic slat actuators 104A, 104B may achieve greater movement within the aircraft wing 100, 400 while taking up less space in the direction of slat 710 movement (e.g., chordwise 152, 452). Furthermore, for fixed travel linear hydraulic slat actuators 104A, 104B, the output travel of the actuator output links 108A, 108B, 108C, and therefore the travel of the attached slat 710, can be adjusted via the arm length of the bell crank 106A.
[0054]
[0063] Although the system has been described herein with particular reference to an aircraft system or aerospace vehicle, in other embodiments, the system may be a vehicle other than an aircraft without departing from the essence of the present disclosure.
[0055]
[0064] In addition, in this specification, an instance where an element is "coupled" to another element may include direct and indirect coupling. A direct coupling may be defined as an element coupled to another element and having some contact with the other element. An indirect coupling may be defined as a coupling between two elements that are not in direct contact with each other and have one or more additional elements between the coupled elements. Furthermore, in this specification, fixing one element to another element may include direct fixing and indirect fixing. In addition, as used herein, "adjacent" does not necessarily mean contact. For example, one element may be adjacent to another element without contacting it.
[0056]
[0065] As used herein, a system, device, structure, article, element, component, or hardware that is "configured to" perform a particular function is in fact capable of performing that particular function without any modification, rather than merely having the potential to perform that particular function after further modification. In other words, a system, device, structure, article, element, component, or hardware that is "configured to" perform a particular function is specifically selected, created, implemented, utilized, programmed, and / or designed for the purpose of performing that particular function. As used herein, the phrase "configured to" refers to the existing characteristics of a system, device, structure, article, element, component, or hardware that enable the system, device, structure, article, element, component, or hardware to perform a particular function without further modification. In this disclosure, a system, apparatus, structure, article, element, component or hardware described as being "configured to" perform a particular function may additionally or alternatively be described as being "adapted to" and / or "operative to" perform that function.
[0057]
[0066] The flow diagrams contained herein are generally defined as logical flow diagrams. As such, the illustrated order and numbered steps are indicative of one embodiment of the presented method. Other steps and methods may be envisioned that are equivalent in function, logic, or effect to one or more steps or portions of steps of the illustrated method. In addition, it is understood that the format and symbols used are provided to describe the logical steps of the method and are not intended to limit the scope of the method. Although various types of arrows and lines may be used in the flow diagrams, these are not intended to limit the scope of the corresponding method. In fact, some arrows or other connectors may be used only to indicate the logical flow of the method. For example, arrows may indicate an unspecified amount of waiting or monitoring time between recited steps of the illustrated method. In addition, the order in which a particular method is performed may or may not strictly follow the order of the corresponding steps shown.
[0058]
[0067] Unless otherwise indicated, the terms "first," "second," etc. are used herein merely as labels and are not intended to impose any sequential, positional, or hierarchical requirements on the items they refer to. Moreover, a reference to, for example, a "second" item does not require or preclude the presence of, for example, a "first" or lower numbered item and / or, for example, a "third" or higher numbered item.
[0059]
[0068] Although the system and method of operation have been described with reference to specific examples, those skilled in the art will recognize that various modifications are possible and equivalents may be substituted without departing from the scope of the claims. Thus, the methods and systems are not limited to the specific examples disclosed, but the disclosed methods and systems are intended to include all embodiments that fall within the scope of the appended claims.
Claims
1. A wing (100) for an aircraft, comprising: fixed structure (102); a linear hydraulic slat actuator (104) mounted to the fixed structure (102), the linear hydraulic slat actuator (104) being oriented spanwise along the aircraft wing (100); Actuator output link (108); a slat (710) attached to the actuator output link (108); and a bell crank (106) coupled to the linear hydraulic slat actuator (104) and to the actuator output link (108); 1. An aircraft wing (100), wherein in response to spanwise movement of the linear hydraulic slat actuator (104), the bell crank (106) is configured to move the actuator output link (108) in different directions to enable the slat (710) to move between a retracted position (610) and an extended position (620).
2. The bell crank (106) is a first arm (810) coupled to the linear hydraulic slat actuator (104), a first length of the first arm (810) defining a first bell crank radius (816); and 2. The aircraft wing of claim 1, comprising: a second arm coupled to the actuator output link, the second arm having a second length that defines a second bell crank radius.
3. 3. The aircraft wing of claim 2, wherein an input stroke length associated with the linear hydraulic slat actuator is based on the first bell crank radius and an output stroke length associated with the actuator output link is based on the second bell crank radius.
4. 3. The aircraft wing of claim 2, wherein the first bellcrank radius is similar to the second bellcrank radius.
5. 3. The aircraft wing of claim 2, wherein the first bellcrank radius is different than the second bellcrank radius.
6. 6. The aircraft wing of claim 5, wherein the second bellcrank radius is greater than the first bellcrank radius.
7. 6. The aircraft wing of claim 5, wherein the second bellcrank radius is less than the first bellcrank radius.
8. 2. The aircraft wing (100) of claim 1, wherein the linear hydraulic slat actuator (104) drives the bell crank (106).
9. 2. The aircraft wing (100) of claim 1, further comprising a support rib coupled to a pivot point of the bell crank (106).
10. 10. The aircraft wing (100) of claim 9, wherein the support rib is further coupled to the linear hydraulic slat actuator (104), the support rib corresponding to the fixed structure (102).
11. The aircraft wing (100) of claim 1, wherein the fixed structure corresponds to a leading spar, a beam, or a support rib.
12. A method (900) for manufacturing an aircraft wing (100), comprising the steps of: Attaching (902) a linear hydraulic slat actuator (104) to a fixed structure (102), the linear hydraulic slat actuator (104) being oriented spanwise along a wing (100) of the aircraft; Coupling (904) a bell crank (106) to the linear hydraulic slat actuator (104); coupling (906) an actuator output link (108) to the bell crank (106); and attaching (908) a slat (710) to the actuator output link (108); In response to spanwise movement of the linear hydraulic slat actuator (104), the bell crank (106) moves the actuator output link (108) in different directions enabling the slat (710) to move between a retracted position (610) and an extended position (620).
13. 13. The method (900) of claim 12, wherein the linear hydraulic slat actuator (104) is coupled to a first arm (810) of the bellcrank (106) and the actuator output link (108) is coupled to a second arm (820) of the bellcrank (106), a first length of the first arm (810) defining a first bellcrank radius (816), and a second length of the second arm (820) defining a second bellcrank radius (826).
14. 14. The method (900) of claim 13, wherein an input stroke length associated with the linear hydraulic slat actuator (104) is based on the first bell crank radius (816) and an output stroke length associated with the actuator output link (108) is based on the second bell crank radius (826).
15. 14. The aircraft method (900) of claim 13, wherein the first bellcrank radius (816) is similar to the second bellcrank radius (826).
16. 14. The method (900) of claim 13, wherein the first bell crank radius (816) is different from the second bell crank radius (826).
17. 17. The method (900) of claim 16, wherein the second bell crank radius (826) is greater than the first bell crank radius (816).
18. The method (900) of claim 12, wherein the linear hydraulic slat actuator (104) drives the bell crank (106).
19. The body, as well as An aircraft comprising an aircraft wing (100) attached to the fuselage, the aircraft wing (100) comprising: fixed structure (102); a linear hydraulic slat actuator (104) mounted to the fixed structure (102), the linear hydraulic slat actuator (104) being oriented spanwise along the aircraft wing (100); Actuator output link (108); a slat (710) attached to the actuator output link (108); and a bell crank (106) coupled to the linear hydraulic slat actuator (104) and to the actuator output link (108); In response to spanwise movement of the linear hydraulic slat actuator (104), the bell crank (106) is configured to move the actuator output link (108) in different directions enabling the slat (710) to move between a retracted position (610) and an extended position (620).
20. The bell crank (106) is a first arm (810) coupled to the linear hydraulic slat actuator (104), a first length of the first arm (810) defining a first bell crank radius (816); and 20. The aircraft of claim 19, comprising a second arm (820) coupled to the actuator output link (108), a second length of the second arm (820) defining a second bellcrank radius (826).